CN108885450A - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN108885450A CN108885450A CN201780013045.4A CN201780013045A CN108885450A CN 108885450 A CN108885450 A CN 108885450A CN 201780013045 A CN201780013045 A CN 201780013045A CN 108885450 A CN108885450 A CN 108885450A
- Authority
- CN
- China
- Prior art keywords
- signal
- microcontroller
- aircraft
- fpga core
- electronic device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004891 communication Methods 0.000 claims abstract description 5
- 238000004422 calculation algorithm Methods 0.000 claims description 9
- 238000012544 monitoring process Methods 0.000 claims description 8
- 238000007689 inspection Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 description 9
- 238000004088 simulation Methods 0.000 description 8
- 230000006870 function Effects 0.000 description 7
- 238000013461 design Methods 0.000 description 6
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 230000004913 activation Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 238000013500 data storage Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0421—Multiprocessor system
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0055—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements
- G05D1/0077—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots with safety arrangements using redundant signals or controls
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/40—Bus structure
- G06F13/4004—Coupling between buses
- G06F13/4027—Coupling between buses using bus bridges
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L12/40006—Architecture of a communication node
- H04L12/40032—Details regarding a bus interface enhancer
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L12/00—Data switching networks
- H04L12/28—Data switching networks characterised by path configuration, e.g. LAN [Local Area Networks] or WAN [Wide Area Networks]
- H04L12/40—Bus networks
- H04L2012/40267—Bus for use in transportation systems
- H04L2012/4028—Bus for use in transportation systems the transportation system being an aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- Theoretical Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Computer Hardware Design (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Feedback Control In General (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
- Safety Devices In Control Systems (AREA)
- Programmable Controllers (AREA)
Abstract
The present invention relates to a kind of aircraft, its electronic device that operating element is used for at least one component and at least one, wherein electronic device has at least one interface, the signal for being used for operating element is provided by means of the interface, wherein electronic device has the combination being made of at least one microcontroller and at least one FPGA core, at least one microcontroller and at least one FPGA core are connected to each other by communication connection, wherein FPGA core can be configured to, so that the configuration according to FPGA core is capable of handling different signals.
Description
Technical field
The present invention relates to a kind of aircraft, at least one component and at least one for operating element
Electronic device, wherein electronic device has at least one interface, and the signal for being used for operating element is provided by means of the interface.
Background technique
The application of known so-called remote electronic device (REU), the remote electronic device are modified from the prior art
For specific application, to be only used for affiliated electrical interface.
Herein disadvantageously, electrical interface only with the interface compatibility of certain types of sensor or simulation or be simply possible to use in manipulation
Specific driving element or other component.
Therefore, according to the prior art, same electronic device is used for different application only is very restricted or can not
Can.
Summary of the invention
Therefore, the present invention is based on purpose be, improve beginning propose type aircraft so that with known in the state of the art
Electronic device compare, electronic device can be more flexibly used.
The purpose is realized by the aircraft of the feature with claim 1.It proposes accordingly, electronic device has by extremely
The combination that a few microcontroller and at least one FPGA core are constituted, the combination are connected to each other by communication connection, wherein
FPGA core can be configured to, so that the configuration according to FPGA core is capable of handling different signals.
The FPGA that abridges indicates field programmable gate array (Field Programmable Gate Array).
Since FPGA core is configurable or has the fact that configurable interface, the use of electronic device is not secured to specific answer
With.More precisely, combined electronic device can be configured for operating element, such as driving element, so that it is functional
The component to be manipulated can be matched with and/or signal can be matched with, the signal is for example supplied to electricity by sensor or other interfaces
Sub-device.
Therefore, following possibility is realized：The electrical interface that electronic device is universally configured according to application makes it possible to assess not
The sensor or analog interface of same type, and/or different driving elements can be manipulated.
Therefore, same electronic device is able to use in different application.
Preferably, electronic device is used for the driving element of aircraft, such as the position of executing agency adjusts and manipulates, with
And be also used in the data set of electric signal, the electric signal is obtained from configurable interface.
Preferably, electronic device is mountable or is integrated in around the component of aircraft to be manipulated, such as in driving element,
It is also mountable or be integrated in the ambient enviroment of the control element of pilot on flight control surface, in undercarriage region.
Herein it is noted that term " manipulation " should widely understand, and also comprising adjusting other than control unit
Or monitoring part.
Electronic device due to its be directed to different application situation configurability, such as manipulate and adjust driving element or
It also for the configurability in the data set of electric signal, can be configured flexibly, the electric signal is for manipulating and monitoring flight
The component of device.
Described by such as starting, electronic device includes the group that at least one is made of microcontroller and one or more FPGA cores
It closes, the FPGA core has configurable signal association structure, and wherein both parts preferably satisfy following function：It is excellent at one
In the design scheme of choosing, FPGA core has configurable interface according to application, provides for other purposes for electronic device
Signal, and/or neutralize information via data bus transmission for data set to other aircraft computers, such as be transferred to and hold
Row mechanism controls unit, is transferred to flight-control computer etc..It is therefore preferred that electronic device is on the output side at least one
A data/address bus connection, or communicated via data/address bus with one or more computers of aircraft.
In a preferred design scheme, FPGA core, which provides integrated signal, to be used in the system of safety-critical make
With.
Microcontroller or microcontroller core are preferred for：Computation-intensive is executed using the interface message provided by FPGA
Algorithm.
In another design scheme of the invention, microcontroller core is established dedicated for the signal or device of safety-critical
The integrality of adjustment mechanism, and automatically execute the selection of the undercarriage of such as high-lift system or the driving unit of wing flap
Monitoring function.
In the preferable design of the present invention, microcontroller core activation system (power up) institute when connecting
The inspection needed, and using for safeguarding necessary application, such as failure data storage, or also unit state via number
According to the transmission of bus.
In the preferable design of the present invention, electronic device includes for the configurable associated machine of signal
Structure.That is, the quantity for being conveyed to FPGA core or microcontroller core or the signal of the two cores can be via simple setting
Option is configured and is adjusted.
In the preferable design of the present invention, position of the combined electronic device for the driving element of aircraft
Adjusting and manipulation are set, and is also used in data set of the electric signal by means of configurable interface.
As described above, combination of the electronic device based at least one microcontroller He at least one FPGA core, wherein
FPGA core is mainly used as I/O (I/O processor) or data concentrator and can correspondingly be configured according to application.This meaning
, it can be according to application preferably by the way that load applies IP kernel to operate different sensors on identical electrical interface in FPGA
Or other interfaces, i.e. signal source.It for example can be analog signal, LVDT, parsing by the signal that these interfaces or sensor provide
Device or discrete signal etc..
The signal or data for being passed to electronic device in this way for example can be on the data/address bus of external number
Transmission, or can also be provided within electronic device, for position adjusting and monitoring function.Here, microcontroller is responsible for
Execute mathematical algorithm and function for monitoring.
In addition, electronic device according to the present invention is preferably able to meet the typical case awing of the assessment for key signal
Safety requirements, and provide the assessment on the data bus.Data/address bus can with aircraft it is one or more other
Computer connection, executes the assessment of the information provided by means of data/address bus on the computer.
Microcontroller core can also execute independent inspection relative to the signal for being transferred to FPGA core or also compare.It is independent
Inspection and comparing can also be carried out relative to the redundant signals of the input signal about FPGA core.Be conveyed to FPGA core and/or
The quantity of the signal of microcontroller core can be as described above via the simple determining option for configuration or via corresponding
Mechanism is configured and is adjusted.
Its advantage is that implement with small space requirement and the technology can be applicable at small shell.
The present invention compared with the existing technology the advantages of be, according to configuration electronic device flexible in application.That is, same
Electronic device can be used in manipulating or adjust driving element, and assessment and data concentration for electronic signal, the signal
For manipulating and monitoring the control element etc. of flight control system or pilot.
Outputting and inputting for electronic device can be according to configuring flexible in applicationly, it follows that electronic device flexibly makes
Use possibility.
Generally speaking, weight aboard is also obtained by the way that unique type of device is used for different application to save and subtract
Few wiring expends, and the advantages of obtain simple-to-maintain.The combination energy according to the present invention being made of microcontroller and FPGA
Enough realize general use.
As other advantage, the integrality of the signal by guaranteeing safety-critical, also obtain be for safety-critical
The application of system.
Detailed description of the invention
Other details and advantage of the invention are elaborated according to the embodiment being shown in the accompanying drawings.
Attached drawing is shown：
Fig. 1 shows the schematic diagram of the electronic device of aircraft according to the present invention；And
Fig. 2 shows the schematic diagrames of the electric installation of aircraft according to the present invention in another embodiment.
Specific embodiment
Use for electronic equipment appended drawing reference 100 indicates in Fig. 1.Appended drawing reference 10 indicate crucial and non-key interface or
Sensor, wherein being provided with crucial and non-key interface or sensor in the 10a of region and being provided in the 10b of region
Non-key interface or sensor provide its signal.
As from further learning in attached drawing, the discrete of power switch 111 is transferred to according to the non-key signal of 10b
Input/output module (In/Out) or be transferred to the input/output module (Input/Output) 112 of simulation.Corresponding feelings
Condition is suitable for crucial and non-key interface or sensor 10a, is equally transferred to unit 111 and 112, wherein this two
Configurable signal associated apparatus 60 is provided between a component.Therefore, electronic device preferably remove microcontroller 30 and one or
Also there is the mechanism for configurable signal associated apparatus 60 other than multiple FPGA cores 20.
Appended drawing reference 50 indicates that simulation and discrete input, the input are fed to one or more microcontrollers
30。
FPGA 20 has configurable interface according to application, and the interface is for providing signal, for its of electronic device
He applies, or neutralizes for data set information being transferred to other aircraft computers, such as executing agency via data/address bus 110
Control unit, flight-control computer.Corresponding communication is indicated with reference number C in the accompanying drawings.The another object of FPGA core 20
It is to provide integrated signal, for the application in the system of safety-critical.
Microcontroller core 30 is used for：The algorithm of computation-intensive is executed using the interface message provided by FPGA.In order to hold
The row algorithm and function, use unit 32.The appended drawing reference 31 of microcontroller 30 indicates monitor part.
Microcontroller 30 is applied not only to close based on being implemented via the interface message that connection provides by FPGA 20 and being executed to calculate
The algorithm of collection type, and be also used for establishing the integrality of the dedicated adjustment mechanism of signal or device for safety-critical, and
Automatically execute the monitoring function of selection, such as driving unit.In addition, 30 activation system of microcontroller core is necessary when connecting
It checks, and using for safeguarding necessary application.
As being described above, unit 60 should be conveyed for configuring with the quantity of adjustment signal, the quantity
It is conveyed to the two cores to FPGA core 20 and microcontroller core 30 or in combination.The quantity of signal can be via simple
Determination option configuration and adjustment.
In the accompanying drawings appended drawing reference 90 indicate electronic control unit, and appended drawing reference 80 indicate electronic unit 100 via
Numeral input 70 is cut off.Appended drawing reference US indicates optional shutdown and appended drawing reference S indicates shutdown, is used to cut off electronics dress
It sets.
Through the invention it is possible that for example FPGA is set by loading IP (intellectual property) caryogamy, so that in electronic device
Identical electric port or interface on can operate or be connected with depending on the application different interface or sensor, that is to say, that for example
It is capable of handling analog signal, LVDT (linear variable difference transformer) etc..
Fig. 2 shows another embodiments, wherein the identical element of identical or function is equipped with and attached drawing mark identical in Fig. 1
Note.
One or more sensors are directly connected in microcontroller 30 via simulation and discrete input 50.
Microcontroller 30 has configurable data concentrator.
Attached drawing shows application of the device 100 for example for the executing agency shown in manipulating, and wherein interface is matched as follows
It sets, executing agency is enabled to be manipulated and monitored by device 100.
Amplitude needed for the operation for LVDT of excitation voltage and frequency have variable voltage and frequency via general
The simulation output end of rate is provided by means of the calculation method realized in FPGA 20.In order to read and assess LVDT signal voltage,
Correspondingly configured using the dedicated assessment algorithm of LVDT one of simulation input used generally applicablely in FPGA 20 (such as
It is suitable for voltage measurement, current measurement, frequency measurement, resistance measurement ...), wherein the LVDT voltage signal is needed for true
Determine the position LVDT.Manipulation control electric current needed for servo valve present in executing agency is defeated via the simulation used generally applicablely
It provides one of out, wherein setting the control electric current of FPGA 20 using the algorithm for being exclusively used in application.
Needed for the present embodiment, for ensure integrality and monitor executing agency signal, via microcontroller 30 can
The simulation input (being for example adapted for voltage measurement, current measurement, frequency measurement, resistance measurement ...) universally used by means of
The dedicated program of assessment algorithm is handled.In the present embodiment, it is related to the current measurement of LCDT signal and servo valve manipulation.?
The manipulation of model selection valve shown in embodiment is executed by means of one of multiple discrete outputs, and for example can be in failure
In the case of according to the requirement of microcontroller 30 interrupt, wherein the model selection valve is configured to solenoid valve.For executing agency
Institute's preparative is run via the data/address bus exchange between microcontroller 30 and FGPA 20 and as needed via outside
Data/address bus provide.
Claims (10)
1. a kind of aircraft is used to manipulate the electronics dress of the component at least one component and at least one
It sets, wherein the electronic device has at least one interface, provides the signal for manipulating the component by means of the interface,
It is characterized in that, the electronic device has the combination being made of at least one microcontroller and at least one FPGA core,
At least one microcontroller and at least one FPGA core are connected to each other by communication connection, wherein the FPGA core can configure
For so that the configuration according to the FPGA core is capable of handling different signals.
2. aircraft according to claim 1, which is characterized in that the component is the driving element of the aircraft.
3. aircraft according to claim 1 or 2, which is characterized in that the FPGA core can apply IP kernel by load
To configure.
4. aircraft according to any one of the preceding claims, which is characterized in that the signal for being applied to the interface is
Analog signal, digital signal, LVDT, resolver or discrete signal.
5. aircraft according to any one of the preceding claims, which is characterized in that described device has at least one defeated
Outlet, the data bus communication of the output end and number, wherein the output end and the microcontroller and and FPGA core
Connection, and wherein the data/address bus is communicated with one or more computers of the aircraft.
6. aircraft according to any one of the preceding claims, which is characterized in that the FPGA core is configured to, for collecting
In multiple data and/or transmit a signal to the microcontroller.
7. aircraft according to any one of the preceding claims, which is characterized in that the microcontroller is configured to, and utilizes
Algorithm is executed by the signal that FPGA core provides.
8. aircraft according to any one of the preceding claims, which is characterized in that the microcontroller is configured to autonomous
Ground executes monitoring function.
9. aircraft according to any one of the preceding claims, which is characterized in that the microcontroller is structured to
Start the inspection of the component.
10. aircraft according to any one of the preceding claims, which is characterized in that exist and closed for configurable signal
The mechanism of connection can transmit signal to the FGPA core by means of the mechanism or be conveyed to the microcontroller.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102016002126 | 2016-02-24 | ||
| DE102016002126.8 | 2016-02-24 | ||
| PCT/EP2017/000251 WO2017144176A1 (en) | 2016-02-24 | 2017-02-22 | Aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108885450A true CN108885450A (en) | 2018-11-23 |
| CN108885450B CN108885450B (en) | 2022-05-27 |
Family
ID=58162501
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780013045.4A Active CN108885450B (en) | 2016-02-24 | 2017-02-22 | Aircraft with a flight control device |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20190047723A1 (en) |
| EP (1) | EP3411767B1 (en) |
| CN (1) | CN108885450B (en) |
| DE (1) | DE102017001740A1 (en) |
| WO (1) | WO2017144176A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3764235B1 (en) * | 2019-07-12 | 2022-10-26 | Ratier-Figeac SAS | Field programmable gate array (fpga) having dissimilar cores |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110054721A1 (en) * | 2007-02-16 | 2011-03-03 | Intelligent Automation Corporation | Vehicle monitoring system |
| CN103611324A (en) * | 2013-11-14 | 2014-03-05 | 南京航空航天大学 | Unmanned helicopter flight control system and control method thereof |
| CN104331086A (en) * | 2014-11-06 | 2015-02-04 | 国家电网公司 | Flight control system of small multi-rotor for power line patrol |
| CN204231422U (en) * | 2014-12-02 | 2015-03-25 | 马正方 | neuron device |
| CN105138495A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | ARINC659 bus controller with embedded microcontroller |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020045952A1 (en) * | 2000-10-12 | 2002-04-18 | Blemel Kenneth G. | High performance hybrid micro-computer |
| US6760898B1 (en) * | 2002-02-22 | 2004-07-06 | Xilinx, Inc. | Method and system for inserting probe points in FPGA-based system-on-chip (SoC) |
| US8666257B2 (en) * | 2007-05-24 | 2014-03-04 | Finisar Corporation | Optoelectronic devices with intelligent transmitter modules |
| CN102209942A (en) * | 2008-09-06 | 2011-10-05 | 洛德公司 | Motion control system with digital processing link |
| US8643539B2 (en) * | 2008-11-19 | 2014-02-04 | Nokomis, Inc. | Advance manufacturing monitoring and diagnostic tool |
| FR2996657B1 (en) * | 2012-10-09 | 2016-01-22 | Sagem Defense Securite | CONFIGURABLE GENERIC ELECTRICAL BODY |
-
2017
- 2017-02-22 CN CN201780013045.4A patent/CN108885450B/en active Active
- 2017-02-22 DE DE102017001740.9A patent/DE102017001740A1/en not_active Ceased
- 2017-02-22 WO PCT/EP2017/000251 patent/WO2017144176A1/en active Application Filing
- 2017-02-22 EP EP17707172.7A patent/EP3411767B1/en active Active
- 2017-02-22 US US16/079,175 patent/US20190047723A1/en not_active Abandoned
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110054721A1 (en) * | 2007-02-16 | 2011-03-03 | Intelligent Automation Corporation | Vehicle monitoring system |
| CN103611324A (en) * | 2013-11-14 | 2014-03-05 | 南京航空航天大学 | Unmanned helicopter flight control system and control method thereof |
| CN104331086A (en) * | 2014-11-06 | 2015-02-04 | 国家电网公司 | Flight control system of small multi-rotor for power line patrol |
| CN204231422U (en) * | 2014-12-02 | 2015-03-25 | 马正方 | neuron device |
| CN105138495A (en) * | 2015-07-31 | 2015-12-09 | 上海卫星工程研究所 | ARINC659 bus controller with embedded microcontroller |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108885450B (en) | 2022-05-27 |
| US20190047723A1 (en) | 2019-02-14 |
| EP3411767A1 (en) | 2018-12-12 |
| WO2017144176A1 (en) | 2017-08-31 |
| EP3411767B1 (en) | 2022-05-25 |
| DE102017001740A1 (en) | 2017-08-24 |
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